.Ii i-~ w= ' STIFFENED EA TED CONNECTION ~= TO COLUMN …...stiffened ea ted connection to column...

I I I I I I I

1 I I I I I I t I I I

C' -" .Ii

i-~ w= '" -~=

RR1482

7627

STIFFENED EA TED CONNECTION

TO COLUMN WEBS

PHA E THREE

DUANE . ELLIFRITT

ANDREW S. MILLER

DEPARTMENT OF CIVIL ENGINEERING

tr IVERSITY OF FLORIDA

GArNE VILLE. FLORIDA 32611

UF PROJECT NO 4504429

FNAL REPORT TO TIlE

A!vIERICA'IINSTJTUTE OF STEEL CO. STRUCTION. INC

April 1994

I I I I I I I I I I I I I I I I I I I

•

TIFFENED SEATED CONNECTION

TO COLUMN WEBS

PBA ETHREE

DANE. ELLlFRiTT

ANDREW. MLLLER

DEPARTMl: T OF CIVIL ENGINEERING

UNIVERSITY OF FLORIDA

GAINl:SVILLE, FLORIDA 32611

UF PROJECT NO 4504429

FINAL REPORT TO 11{E

AMERICAN INSTITlITE OF TEEL CO STRUCTIO • INC

April 1994

I· I I I I I I I I I I I I I I I I I I

ACKNOWLEDGEMENTS

Funding for this research was provided b the Amencan InSlltute of teel

Construction, Inc .. Chicago, illinOIs.

The test specimens were supplied by wen teel Company of Flonda.

Jacksonvtlle, Florida. Whitley Steel. Lawtey, Florida provided the top angles and vanous

plates used throughout testing

The authors would like to also acknowledge David Ricker and William Thornton

for their helpful suggestions.

The assistance oftechnichians Danny Richardson, Bill Studstill , Ed Dob on, and

Hubert Martln,and student assistant Carl Delee In the Civil Englneenng Structures and

Materials Laboratory at the University of Florida, is gratefully acknowledged

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I I I I I I I I I I I I I I I I I

TABLE OF CO TENTS

OME CLA TURE ................................... .. ................................................................ IV

INTRODUCTION .... ... ... .. ........................... ....................... ........................................... ..... I

PHASE n IREE LABORATORY TESTING ............... ....................................... . .......... 3

Introduction ... . .................................................. ........................... .. ..................... 3

Part One....... . ........................................................................... .. ...................... 5

Part Two .. " .. " ....... " ...... .............................................. '"'''''''''''''''''''''' 8

Phase Three Test Results ... ................ .. ...................... ........................................... 9

Pan One ... .. .. """"""'" ......... ... ... ... .......................... .... ............... , ...... .... , ...... 9

Part Two ............ ... .......... .. ....... .. .. .. .... ........... ... ...... ..... ............. .... ... ........... 12

Calculation of Load on II fTened Seats .. ....... .. .... .. .. """'''''''' ............... .. .............. 15

Tabulated Results ... ...... .. ....... ...... ...... ...... ......... .. .. ....... .. ... .. .. .. ..... .... ...... ............... . 17

Material Properties .... ... ....................... ... ... .. ....... ............ .. ....... .. ........ ....... , .. .......... 21

CONCLUSION ..... ... .. ..... ....... ... .................... ............... .. ................... ................ .. .............. 21

Sti fTener Buckl i ng ............. .... ....... ..... ..... ... .... ... ... ... ... .... .. ...... ....... ... ..... ...... .. .. ...... . 22

Extended Seats ........ ..... ................... .... , ... ......... ........ .. ..... ...................................... 23

Welded vs Bolted Connection ... ...... .. ... ... ..... .. .. .. .. ... .... ...................... ..... .. ............ . 24

Beam Web Yielding ... ............................................................. """'"'' ...... '"'''''''' . 24

Design Recommendations ........... .... .. .................................................................. 24

Further Research '"'' ....... .................................. , .. """".""."." .. ". '"'' .............. ..... 25

•••

• • • • • • • • • • • • • • • I

• •

APPENDICES

A Firute Element AnalysIs of 16 Inch ufTener.. ...... ....... .......... ......... 26

B: Part One Displacement v Reaction Graphs .................................................. .. 40

C: Part Two Displacement v Reaction Graphs ................................................... 55

D: Beam Web Stress and Strain Graphs.... ......................................... ........... .. 66

REFERE CES.... .......... ........................................ ........... .... ....................................... .. 75

iii

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1 1 1 1 1 1 1 1 1 1 1 1 1 1 I 1 1

NOMENCLATURE

Aw ------------------ Total weld length

.---Connection seat plate width

Ix --------Moment of Inerlla about x-a.'os

Fu --- - Ultimate stress of steel

Fy ---- --- Yield stress of steel

Ls -- ----- Length of connection stiffener

P -----------Applied load

PASD -------------ASD design load on connection

PFArr. ----------Test failure load

PULT --------Ultimate load based on weld strength

Rw Weld allowable stress

Sx Section modulus about x-axis

W --- Stiffener width

W' ----------------Extended seat plate length

e --- Eccentricity of load

.-------Seat plate thickness

y ------- Location of centroid with respect to y-axis

iv

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1 1 1 1 1 1 I I 1 I I I I 1 I I I I

INTRODUCTION

This phase of the research of stiffened seated beam connections to column webs

consisted of tests which were suggested by the Research Committee of AlS . These

tests were performed to "fill In the holes" left b Phases One and Two, since It was felt

that the previous phases of research did not deal with completely realistic eat and

Stl ffener sizes.

Phase One (Ellifnn. Sputo, 1989) consisted of tests of four different stlfTener

configurations welded to the webs of four different Wide flange columns. The Wide

flange sections used as columns dunng this phase, however, were actually tandard beam

sections. These type of sections were used for their thin webs In order to achieve large

rotations of tbe seat. Phase One was, therefore, more of a pilot stud used to ee wbat

methods of analysis and deSign might work well for this type of connection.

Phase Two (Ellifrin Sputo, 1990) consisted of tests of more realistic eat

configurations welded to more realistic column sections. Sixteen tests were performed ID

all using various means of attacbing tbe seat to the column web and the beam to the seal

During Phase Three, the more commonly used ratio of stl fTener depth-to-wldth

ratio of 2: I was used, with one case tested with a stiffener depth-to-Wldtb ratio of 4: I.

Also tested during this phase of research were seats using plates that extended be ond the

stiffener width witb erection bolts placed beyond the stiffener as well All columns were

WI4x61 sections which is a typical column section.


The object of Phase Three testing was to test more realistic seated connections,

which are already being used in the field, to determine If the AISC method for deSigning

these connections IS adequate and realistic. As well, Phase Three testing was to

determine how the web of the beam connected to a column using a stiffened eated type

connection might be affected. In other words. It was to be determined whether beam web

Yielding or crippling was a problem at service conditions.

Phase Three testing actually consisted of two parts. The first part of the testing

took place dunng June and July of 1993. The second part of the testing took place In

January and February of 1994. Dunng the first part of Phase Three, the load was

poSItioned at the quarter point of the reaction beam. With this arrangement, however, the

connections did not fail , due to the oversized welds provided on our test speCimens, and

the limitations of our testing equipment.

For the second part of Phase Three, the load was moved as close to the seated

connection as was physically possible. This means that the load was positioned at 13.5

Inches from the right end of the reaction beam. The reaction beam was also raised at the

right end in an attempt to simulate the same end rotation at the right end of the beam at

ultimate load as in tbe previous tests. Two 3/4 inch plates were welded in place under

the column raising the beam seat by I ~ inches

Please refer to Phases One( 1989) and Two( 1990) for specific results of those

phases and discussions of previous studies in this area.

2


PHASE THREE LABORATORY TESTING

Introduction

Phase Three testing conSISted of IX specimens that used WI4x61 column

eClions. Tests One, Two, and Three used beam seat plates of 3/8 in. thickness. Tests

Four, Five, and Six used beam seat plate thickne s of 1 _ in., J/4 in ,and J 8 In

respecttvely A 16 in. stiffener was used for Te t Two. All other tests performed ulilized

8 in. sllffeners. Tests Three, Four, and Five used beam seat plates which extended three

Inches beyond the sllffener width. All beam seats were SIX Inches WIde and u ed

ttffeners that were four Inches In width.

The reaction beam used In this phase of testing was the same one used In phases

one and two. It was a welded girder fabricated from 70 ksi steel. The flanges were

6in.x3/4in. plates, and the web was a 14in.xll2in. plate. High strength steel was selected

in order to limit the depth of the girder, thus enabling end rotations of magnitudes typical

to beams in floor systems while sull providing sufficient strength for testing purposes.

Figure I depiCts and lists the dimensions of the specimens tested, and a dra\ inS of the

load and suppon configuration can be seen in Figure 2.

3

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•

Test

2

3

4

5

6

Bs

3.50"

W

4"

4"

4"

4"

4"

4"

All columns are W14 x 61

All stiffeners are 3/8"

2.75"

W

fu 15 b

6" 3/8" 8"

6" 3/8" 16"

6" 3/8" 8"

6" 1/2" 8"

6" 3/4" 8"

6" 3/8" 8"

Figure I. Seat Dimensions for Phase Three

W'

5.50"

w

W'

7"

7"

7"

I I I I I I I I I I I I I I I I I I

Figure 2. Load and Support Configuration

p

/\ r-

L-

'" \ ", 9ft 3ft

Part One

The connection of the beam to the beam seat in tests one through five was

accomplished with 7/8 in. A-325 bolts only. For Test One and two the bolts were placed

2-3/4 in. out from the column face. For Test Three through five the bolts were placed a

distance of 5-1 /2 in. out from the column face. For Test Six, the bolts were placed a

distance of2-3/4 in. out from the column face and 1/4 in. fillet welds were made along

the length of the seat on both sides of the reaction beam. The setup of Test Six was

5

I· I ' I I I I I I I I I I I I I I I I I

idenlteal to Test One except for the weld along the sides of the reaction beam Dunng all

te ts a L4x4xl 4 top angle was welded at Its toes to the top flange of the reaelton beam

and to the column web.

Dunng this ponion of Phase Three tesltng, the web of the reaction beam had

strain gages attached to It in order to assess whether web }'lelding or web cnppllng would

be a problem at seTVIce conditions. The strain gages used were weld mounted gages of

type EA-06-W250A-120 from the Micro-Measurement Division of Measurements

Group. Inc. The gages were indiVIdual gages that were placed in a 4 degree ro ette

configuration by hand. The location of the strain gage rosettes IS shown in Figure 3 A

pbotograpb of the strain gage arrangement is also shown on the next page.

Figure 3 Strain gage rosette placement

Sl8 It

2 ", 2 ft ,

rosette 3 rosette 2 rosette 1

seat

stiffener

6

I :r-c£. w

I ~


- BS-i \ 18~

Photograph of Strain Gage Arrangement on Beam Web for Part One

7

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Part Two

The same test specImens, which were previously tested during Part One were

used dunng Part Two of Phase Three. The main difference between the two parts was

the location of the hydrauhc ram used to apply the load as explamed prevIOusly The

other difference was of course that the webs of the test columns had alread yielded

somewhat during the first part of Phase Three. Therefore. when lookmg at the load

dIsplacement graphs m Appendix C, one must keep in mind that the lotal displacement of

the seat and stiffener IS the displacement recorded during Part Two plus any permanent

deformation caused during Part One.

As mentioned previously, the column on which the seats were welded was raised

I ~ mches, thus. achieving nearly the end rotation at ultimate load as in Part One. The

beam curvature from Part One was calculated using the integral of the displacement

formula in the ASD manual for a simply supported beam with a concentrated load at Its

quarter pomt. An method that allows curvature calculations could have been used to

achieve the same results. including the conjugate beam method. This curvature of

O.000065P rad, where P is the ultimate load from Part One, was used to find the required

end displacement at the right end of the beam of 1.87 inches, using P=200 kips. Due to

safety concerns and the fact that the load was still more than one foot from the end of the

beam. however, the column was raised only 1.5 inches by pLacing two 3/4 inch plates

under the column and welding them into place.

8


During this pan of the testing, Test One and Six both used erectIon bolts to attach

the beam to the seal. However. dunng Test One a top angle was not used. ThIS caused

some interesting results which can be seen in Table I and Table 2 later In thIS paper

Phase Three Test Results

Pan One

The test specImens were specIfied to have 1/4" welds attaching the tlffened eats

to the column webs. The specImens were delivered having oversized welds. gIVing them

added strength, not allowing failure u ing our test equipment dunng Pan ne. ProST In

Table I and Table 2 refers to the maximum reactIon that the seat experienced dunng Pan

One of the testing. This maximum value was a function of our testing equIpment, not of

the seat strength.

Before testing, the back of the column web, in the vicinity of the beam eat, was

white washed along with the web of the reaction beam. The cracking of the white wash

howed where yielding had occurred during testing. Yielding of the column web In the

area of the beam seat and stiffener was apparent in all of the tests. Web yielding of the

reaction beam was apparent in all tests as well . This, however occurred at loads well

beyond the service loads of the connections.

Dunng Tests One, Two, and Five, two LVDT's were used to measure

displacement of the beam seat and stiffener. They were placed in contact with the back

of the column web at the elevations of the beam seat and the bonom tIP of the stiffener.

9


The displacement (rotallon) of the beam seat and stiffener may be slightl. exaggerated

for these tests. since, as it was later discovered, there was some rigid body rotation of the

ennre column. This rigid body rotation was unexpected since the column was anached at

the top and bonom to the test frame. Dunng Tests Three. Four, and ix, an additional

L VDT was placed in contact with the left column nange at the elevation of the beam seat

In order to mOnitor the ngld bod motion of the column. A photograph shOWing the three

L VDT arrangement appears on the next page

Graphs shOWing the L VDT displacemenl readings In relation to the seat reaction

are located In AppendiX B. L VDT I was located at the elevation of the seat, L VDT 2

was at the elevation of the bottom of the stiffener, and L VDT 3 was on the column

nange.

Test specimen number two used a stiffener that was 16 inches In lenglh. ThiS was

the test with the stiffener depth to length ratio of 4: L During this test, the stiffener was

observed to buckle inelastically over apprOlumately the top S inches at a load applied to

the reaction beam of 170"-with the reactIOn at the beam seat being 127 Sk This IS seen

as a problem in predicting the strength of th.is connection, since buckling occurs long

before failure is predicted. A photograph of the buckled stiffener is included on page II .

A simple finite element analysis was performed using SST AN, which IS a Simple

PC based structural analysis program created by Dr. Marc HOil Thl ho\~ed that the

stresses in the top four Inches of the stiffener were above the yield stresses The Input

and output from the program is contained in Appendix A.

10

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Photograph Showing Three L VDT Arrangement for Pan One and Pan Two

11

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I I I

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The strain gage rosettes placed on the reaction beam were most effective for the

tesl1ng of speCimens four and five. It was during these tests that the gages were new and

unstrained. The strain data taken from these tests was plotted as principal compressive

strain versus the seat reaC!1on for each rosette location. These plots can be seen 10

Appendix D. A typical stress distribution is also shown in Appendix D. ploltlng principal

stress versus position along the beam.

Part Two

All seats were failed during the second part of testing. Graphs depicting the

displacement of the seat in relation to the reaction of the seat, with the excepl10n of one

for Test Three, are available in Appendix C. The displacement data for Test Three was

lost and was irretrievable when the computer reading the L VDT's crashed after testing

had taken place. Dunng this part of the testing, three L VDT's were used in the same

configuration described in Part One, that is, LVDT I at the level of the seat, LVDT 2 at

the level of the bottom of the stiffener, and L VDT 3 on the right column flange.

During Test One, which was actually the last test run, the top angle was omitted.

This showed the importance of using a top angle as AlSC suggests. By comparing Test

One with Test Six, which was identical to Test One except for the top angle, one can see

that the failure load without a top angle is approximately 20 percent less than when a top

angle is used.

12

", I I I I I I I I I I I I I I I I I I

In fact. in four of the five tests that used top angles. failure of the seat was

preceded by failure of one of the top angle 's welds. It would seem that the use of a top

angle not onl adds stability to the connection, but adds strength as well.

During Test Two. the stiffener reached its buckling load at apprQ)(Jmately 130k

When this happened. the travel of the bottom of the stiffener stopped and reversed

directions as buckling continued. This can be seen from the graph of displacements

measured by L VDT 2 during Test Two. This graph is probably represents more of a

realistic picture of the buckling event than the graph from Part One of the testing. A

photograph of the buckled stiffener after Part Two testing can be seen on the following

page.

In general, failure of the seat was achieved through failure of the weld under the

seat due to very large rotation of the seat. The stiffener remained attached to the column

in all cases. Had loading continued, the seat and stiffener probably would have started to

detach from the web even more through failure of the stiffener welds. Loading was

stopped when large rotations without increase in load over three to five data retrievals

were observed.

13


Photograph of Buckled Stiffener-Test Two, Part Two

14

I' .


First, the follo\~lng method. suggested by mer Blodgen. was used to calculate

the theoretical throat:

b

a

Then. the allo\\able and ultimate loads on the uffened seats tested In thl phase

were calculated In one of two way for each weld slze- 3.8 in x . 16 In or I 4 In " 1,4

In. The loads were calculated for [ub/e I uSing the AI C method and for I'uhle 2 using a

more realistic method. referred to here as the Eilifritt, Sputo, Miller method The main

difference in the two methods I In the weld length along the WIdth of the seat AI C

uses a value of02L on each Side of the stIffener We use a weld length equal to the seat

WIdth minus the stlfTener thickness An example of the formulas u ed follows:

:s


alculation of ectiOD '\lodulu of Weld:

b

T

y

d

alculation of lIowable Load on tiffcner

")d ~ d - ") v= -- 2d +h

d ~

2d+h

2dJ (/'

I, = -)- - 2d + h

I, d 1 + 2dh S = - = --=..:.~

' .~ 3

Method, Ellifritt. puto, Miller Method

R=~pe+ P w • 2.4L

2.4 Ll Rw p - r==:====:=

- .J16e2 + L2 p_ AwS,R.

- ~Awe2 + ;

Where Aw = 2L, +b -I,

It is felt that the Ellifritt, Sputo, Miller method of computing the allowable load

on the seat based on the weld stress IS a more realistic and ne er unconservattve

approach. The AlSC approach, using a weld length ofO.4L under the seat, is

conservative only when the width of the seat plate, Ss. IS 0.8 Ls or larger. The AJSC

method is unconservative for cases other than mentioned above by over predlcitng total

weld length. Although the difference In stress calculations IS mirumal, the use of the

proper weld length does make a dIfference in the numbers which mIght confuse omeone

UStng the AlSC method.

16


Tabulated Results

This section contains test results for both parts of Phase Three. The results are compared

to calculated values of allowable and ultimate loads on the seat. The calculated values

are denved as descnbed In the prevIous section. For the calculations orPA 0 and PI 1.1 for

Tests Three, Four, and Five, and eccentricity equal to 80 percent of the eat length, W' ,

was used instead of 80 percent of the stiffener width, W. This value for eccentricity was

used because the bolts for the extended seat connections were beyond the edge of the

sllffener, and It seemed more rational to base the eccentnclty on the seat length In thiS

case than on the suffener width. Refer to Table I and Table 2 on the next two pages.

In addition to Table I and Table 2, Table 3 shows a comparison of the calculated

values of P ASO and P UtT using the AISC method ad the Ellifritt, PUIO, Miller method.

17

I· I I

Ta ble I. Pbase T bree Test Results ompared witb 15 Value of P \ 0 a nd PIILT

actual ,alues with 3 8 In \ 16 In. welds.

I Test PTEST• PFAII PASD PULT Pr AUJP ASD P,AIL,PULT

149.0k 133. lk .. Sl.3k 102.6k 2.60 I 30

I 2 IS1.6k 177 2k 151.1 k 302.2k I 17 0.59

I J 147.6k 1476k 32.Sk 65.0k 4.53 2.27

I 4 1487k 148.7k 32.5k 65.0k 457 2.29

145.7k 1825k 32.5k 65.0k 5.62 2.SI

I 6 146.9k 166.9k 51 .3k 102.6k 3.25 163

I if 1f4in. x 1(4 In. welds were used as specified:

Test PTEST•

PFAIL PA 0 PULT PFAlLiP ASO PFAIlfPULT

I 1490k 133. lk .. 378k 75.6k 3.52 I 76

I 2 151.6k 177.2k II Uk 222.6k 1.60 O.SO

3 147.6k 147.6k 24.0k 4S.0k 6.16 3.0S

I 4 148.7k 14S.7k 24.0k 4S.0k 6.20 3. 10

• S 145.7k IS2.Sk 24.0k 4S.0k 7.60 3.80

I 6 146.9k 166.9k 37.Sk 75.6k 4.42 2.21

·Part One maximum load

I •• 0 top angle used

I I I 18

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Table 2. Pha e Three Test Results A ompared to Ellifritt. pUIO. \tiller Valu of P o and Pt.'LT

I actual values wIth 3 8 in. x S. 16 in. welds

Test PTEST- PFAIL PASO PULT PFAIV P A'I) PFAIUP 'JLT

I 149.0k I" Ik .. -'-' . 66.Sk 133.0k 1.00 100

I 1 ISI.6k 177 2k 146. lk 292.2k 121 606

3 147.6k 147.6k 43.9k 87.8k 3.36 I 68

I 4 1487k 148.7k 43.9k 87.8k 3.38 169

I 5 14S.7k I 82.5k 43.9k 87.8k 4 16 2.08

6 1469k 1669k

I 66.5k 133.0k 2.50 I 25

if 114m. x 114 in. welds were used as specified:

I Test PTEST- PFAIL PASO PULT PfAlJPASO PfAJJiPULT

I 149.0k 133.1 k .. 49.0 k 98.0 k 2.72 1.36

2 151.6k 177.2k 107.7 k 215.4 k 1.64 0.82

I 3 147.6k 147.6k 32.4 k 64.8 k 4.56 2.28

I 4 148.7k 148.7k 32.4 k 64.8 k 4.58 2.29

5 145.7k 182.5k 32.4 k 64.8 k 5.64 2. 82

I 6 146.9k 166.9k 49.0 k 98.0 k 3.40 1.70

I -Pan One rna irnurn load

I .. 0 lOp angle used.

I I 19

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Table 3 Comparison ofCaiculated Loads from AIS and Ellifritt. puto. Miller (E \1 ) Method

I actual val ues with 3/8 In . x 5116 in. welds:

AI METHOD E M METHOD

I Test PASO PUll PFAU!PASO PFAU!PULT PAS!) PUll PrAll/PASO PFAlJ./'PIlLT

I 51.3 k 102.6k 2.60 1.30 66.5k 1330k 2.00 100

151.1 k 302.2k 2 1.17 0.59 146. lk 292.2k 121 .606

I 3 32.5k 65.0k 4.53 2.27 43.9k 87.8k 3.36 1.68

I ~ 32.5k 65.0k 457 2.29 ~3 . 9k 878k 3.38 169

5 32.5k 65.0k 5.62 2.81 43.9k 878k 416 2.08

I 6 51.3k 102.6k 3.25 1.63 66.5k 133.0k 2.50 1.25

I if 114in. x 1/4 in. welds were used as specified:

I AI METHOD E M METHOD

Test PASO PIlLT PFAU!PASD PFAIJPIlLT PASO PIlLT PrAIJPASD PrAIJPllLl

I 37.8k 75.6k 3.52 1.76 49.0 k 98.0 k 2.72 1.36

I 2 Il l.3k 222.6k 1.60 0.80 107.7 k 2 15,4 k 1.64 0.82

24.0k 48.0k 32,4 k 64.8 k 3 6.16 3.08 4.56 2.28

I 4 24.0k 48.0k 6.20 3.10 32,4 k 64.8 k 4.58 2.29

I 5 24.0k 48.0k 7.60 3.80 32,4 k 64.8 k 5.64 2.82

6 37.8k 75.6k 4.42 2.2 1 49.0 k 98.0 k 3,40 1.70

I I I 20

I

I ' I' I I I I I I I I I I I I I I I I I

Matenal Propenies

Three tensile coupons were cut and milled from the column web of the te t

specimens. These coupons were used to find the strength of the steel used In fnbncatlng

the specimens. It was assumed that the steel used to fabricate the seats and stlfTcners was

of the same strength as the steel used for the columns. A36 steel was peclfied for the

columns and seats Table 3 below hows the results of all three tensile test and the

average of all results.

Table 3. teel Properties

Tensile pecimen Fy (ksi) Fu (ksi) 6UL(%)

I 48.26 70.79 41

2 44.29 64.67 48

3 47.68 71.82 32

G. 46.74 69.09 40

CONCLUSION

The findings of these tests seem to show that the beam seat configurations used in

this phase of testing were supenor to those configurations used in Phase One and Phase

Two As stated before. however, the use of elongated stiffeners WIth a depth to WIdth

21


rallo of 4' 1 or greater hould be studied more closel. due to the problem with buckling of

the slIfTener at servtce load

The findtngs also eem to potnt out that the use of extended eats does not

Improve the overall strength of the connection. It may. 10 fact. decrease the strength of

the conneCllon b tncreastng the effecllve eccentncity of the reacllon on the eat

tiffener Buckling

ThIs buckltng of the sllfTener has been questioned as to whether illS a real

problem stnce the test beam used had a web that was w1der. and had a hIgher YIe ld

strength than the sllfTener, whIch IS not allowed by AlSC speclficallons. The buckling of

the stiffener is most Itkely caused by a stress concentration near the outside comer of the

tlffener encountered when the beam rotates and the bearing area decreases. It is obVIOUS

that the stress concentration would still occur even if a web matching the size and yield

trength of the stiffener were used. It is possible that the beam web would fail before the

stiffener buckled, and it is assumed this is why AISC made this provision. It is obVIOUS

from this limited testing, however, that there is a more complex interaction between

beam, stifTener, and column web when using seated connections with aspect ratios of 4:1

or greater than there is for stifTened seated connections with aspect ratios of2 .1 or

smaller. Therefore, It is belteved that more testing of stifTened beam seats UStng aspect

ratios of 4: I or larger, and posslbl even 3 1, should be done uSing beam webs that match

22

.,: I I I I I I I I I I I I I I I I I I

the Itffener thickness and yield strength. This wa a rational approach to calculaltng the

strength of ItfTened seated connecltons uSing high aspect ratio can be found

Extended Seats

It seems that the Extended seats in Tests Three, Four. and Five do not help the

overall strength of the conneclton, and may, In fact, decrease the overall strength due to

the Increased eccentnclty of the beam reaclton on the seat. This IS eVident b companng

failure reaction values In Tests Three and Four to the failure reaclton In Te t I Test

Five had a larger failure reaclton than Tests Three, Four, and SIX However. 1\ I felt that

this IS because the welds on the top angle did not fail and is probably not due 10 the seat

configuration. It is possible that larger welds than necessaty were used to attach the top

angle in thiS case.

One may note that the ratios PFAI!iP A D and PFAl!iPULT are larger for Tests Three,

Four, and Five than the same raltos for Test Six. This IS due to the value of eccentnclty

used in calculating P ASD for Tests Three, Four, and Five. Ln these case , results were

based on an eccentricity of 80 percent of the seat length W' , since AISC has not yet

adopted a standard for this type of seat configuration. It is possible that using an

eccentricity based on suggesttons from Phase Two would give better results. In other

words, an eccentricity calculated as half the distance between the end of the beam and

the erection bolts plus I inch for beam clearance of the column Oange might Yield

better results. However, more than the three tests used here \~ould have to be completed

23


before one could endorse such a method for computing the eccenmcity of this type of

connecllon.

Welded vs. Bolted Connection

The data seems to show that there is practically no difference 10 strength when

usmg bolts or welds to attach the beam to the seat. This is eVIdent by companng PTFST

for Tests One and Six.

Beam Web Yieldmg

Beam web yielding does not seem to be a problem dunng service conditions and

would not even occur for A36 beams until reactions near the ultimate capacity of the

connection, PULT, were reached. This is evident b observing the graphical stress and

strain data for BS4 and BS5 in Appendix D.

Design Recommendations

It is recommended that stiffened seated connections using stiffeners with a depth

to width ratio of 4: I or greater should not be used if they have been designed using weld

strength as the controlling strength factor.

The ElJifrin, Sputo, Miller method of calculating the weld length for these

connections seems to be a more realistlc approach. It is therefore recommended that this

method be used over AlSC' s method in order to achieve more accurate results.

24


It is also recommended that the code show the option of using erection bolt to

connect beams to the seats In the section of the code \~ere welded tlffened eats are

used.

Further Research

Further Investigation of the use of depth to width ratios of3 .1 and greater IS

suggested. This suggestion is made in light of the buckling incident which occurred

dunng thIs phase of testing wlIh the stiffener In Test Two. The buckling of the stiffener

precedes the predicted ultimate strength, and thus, cuts Into the factor of safety provIded

In ASD. This is seen as a greater problem when LRFD is used.

It is also recommended that research using reaction beams with web thickness

and yleld strength corresponding to the provisions of A1SC be completed In order to

achieve a more rational picture of the beam/seat interaction at failure .

25

I:' I " I I I I I I 1 I I I I I I 1 I I I

Appendix A

Finite Element Analysis of 16 Inch Stiffener

As stated before, a finite element analysis was performed for test two In order to

study the inelastic buckling phenomenon which occurred at a reaction of 127.Sk The

program used for the analysis was SSTAN by Dr. Marc Hoit of the Department of Civil

Engineering, Structures Group, at the University of Florida. The program IS designed for

simple linear structural analysis and does not handle stability problems. The analysis

does, however, give an idea where stress concentrations occur, which are believed to be

responsible for the buckling event. A model of the stiffener showing the node numbenng

and a panial stress distribution is available on the following pages

Notice that most of the stresses are above yield in the top four Inches of the

stiffener and they get larger nearer to the free edge, showing a concentration of

compressive stress in the top right comer of the diagram. Only compressive stresses, Szz

are plotted. The stresses are listed by element and node in the output from SST AN wnich

is included.

The load was modeled as an equivalent distributed load over the width of the

stiffener, W. The stiffener was modeled using 16 nine node, plane stress, membrane

elements which were fIXed along the left edge. Numbering of nodes and elements is

from left to right and top to bottom.

26


,

-~- --

~ 1.1 J'

! 4

.. T .......

zz ~ 1_

27

I.: 1 I 1 I I I I 1 I I I I I I I I I I

,

z

v

..---

,

t4 -: b! '8 -+-~..I-~I-l

38 40 42 44

":71 ":S 5! 53 -+ .................... +-

56 58 60 62 , ,

t _5_ +' :9 r ;'

L~ "4 6 T

3 "'5 "5 ~9 0 1 28

I~


BS2.TXT

SSTAN study of 16 inch stiffener C------------------------------------------------C Calculation of load on each element {Pb) C w=127.S*(12/4)=382.S C Lij=I/12 C C Pb=wLij/30 C C C {S.312S} C Pb={21.2S} C {S.312S}

{ S I {201 {SI

C------------------------------------------------81 , 1 , 1 COORDINATES 1 x=o 2 3 4 S 6 7 8 9 73 74 7S 76 77 78 79 80 81

Y=O Z=O Y=.S Y=I Y=I.S Y=2 Y=2.S Y=3 Y=3.S Y=4 Y=O Z=16 Y=.S Y=I Y= I. S Y=2 Y=2.S Y=3 Y=3.S Y=4

G=l,73,9 G=2,74,9 G=3,7S,9 G=4,76,9 G=S,77,9 G=6,78,9 G=7,79,9 G=8,80,9 G=9,81,9

BOUNDARY 1 ,81 1,73,9

DOF=F,R,R,F,F,F DOF=F,F,F,F,F , F

PLANE 16,1,0 1 E=29600 U=0.30 1 N=I,2,3,10,11,12,19,20,2I,M=1 H=.37S G=4,4

LOADS 1 L=I 2 L=I 3 L=I 4 L=I

F=0,O,S.12S,O,O,O F=O,O,21.2S,O,O,O F=O,O,10.2S,O,0,0 F=O,O,21.2S,O,O,O

29

.' BS2.TXT

•

I 5 L=I F=0,0,IO.25,0,0,0

I 6 L=I F=0,0,21.25,0,0,0 7 L=I F=0,0,IO.25,0,0,0 8 L=I F=0,0,21.25,0,0,0

I 9 L=l F=0,0,5.125,0,0,0

• I I I I I I I I I I I I I 30

I

I, . ittt.t •• tttttt.tt.ttttttttttttt ••• ttttttttttttttt ••• ttit

I "" SST!N - Silple Structural Analysis Progra. , ••• Copyrlgbt 1987 By Dr. Marc Hoit, University 01 Florida ttt.ttttttttttttttttttttttttt t t.t.ttttttt.ttttttttttt.it

I I

SSTAN study 01 16 incb stillener

NUNBER or JOINTS : 81 NUKBER OF DIFrERENT ELENENT TYPES : 1

I KUKBER or LOAD CONDITIONS : I

I HODE BOUIDARY CONDITION CODES NODAL POINT COORDINATES NUKBER I Y ! XI yy Zl I Y Z

1 F F r r r r .000 .000 .000 2 r R R r r r .000 .500 .000

I 3 r R R r r r .000 1.000 .000 4 r R R r r r .000 1.500 .000 5 r R R r r r .000 2.000 .0 00

I 6 r R R r r r .000 2.500 .000 7 r R R r r r .000 3.000 .000 8 r R R r r r .000 3.500 .000

I 9 r R R r r r .000 4.000 .000

10 r r r r F r .000 .000 2.000 11 r R R r r r .000 .500 2.000 12 r R R r r r .000 1.000 2.000

I 13 r R R r F r .000 1.500 2.000 14 r R R r r r .000 2.000 2.000 IS r R R r r r .000 2.500 2.000

I 16 r R R r r r .000 3.000 2.000 17 r R R r r r .000 3.500 2.000 18 r R R r r r .000 4.000 2.000

I 19 r r r r r r .000 .000 4.000 20 r R R r r r .000 .500 4.000 21 r R R r r r .000 1.000 4.000 22 r R R r r f .000 1.500 4.000

I 23 F R R r r r .000 2.000 4.000 24 r R R r r r .000 2.500 4.000 25 r R R r r r .000 3.000 4.000

I 26 r R R r r t .000 3.500 4.000 27 r R R r r r .000 4.000 4.000 28 r r F r r r .000 .000 6.000 29 r R R r r r .000 .500 6.000

I 30 r R R r r r .000 1.000 6.000 II r R R r r r .000 1.500 6.000 32 r R R r r r .000 2.000 6.000

I II r R R r r r .000 2.500 6.000 34 r R R f r f .000 3.000 6.000 35 r R R r r f .000 3.500 6.000

I 36 r R R r r r .000 4.000 6.000 37 r F r r F r .000 .000 8.000 38 F R R r r r .000 .500 8.000 39 r R R r r r .000 1.000 8.000

I 40 r R R r r f .000 1.500 8.000 41 r R R r r r .000 2.000 8.000 42 r R R r r r .000 2.500 8. ODD

I 4l r R R r r r .000 3.000 8.000

1< i4 F R R F F r .000 UOO 8.000 45 r R R r r F .000 4.000 8.000

1 46 F F F F r r .000 .000 10.000 47 F R R r r F .000 .500 10.000 48 F R R F r r .000 1.000 10.000 49 r R R F r F .000 1.500 10.000

1 50 F R R r F r .000 2.000 10.000 51 F R R r F F .000 2.500 10.000 52 F R R r F r .000 3.000 10.000

I 53 F R R F r F .000 3.500 10 .000 54 F R R F F F .000 4.000 10.000 55 F F F F r F .000 .000 12.000 56 F R R r F r .000 .500 12.000

I 51 , R R , F , .000 1.000 12.000 58 r R R F r r .000 1.500 12.000 59 F R R r F F .000 2.000 12.000

I 60 r R R F r r .000 2.500 12.000 61 F R R F r r .000 3.000 12.000 62 r R R r r F .000 3.500 12.000

I 63 r R R r r r .000 4.000 12.000 64 F r r r , r .000 .000 11.000 65 r R R F r r .000 .500 14.000 66 F R R r r F .000 1.000 14.000

1 61 r R R F F r .000 1. 500 14.000 68 r R R F r r .000 2.000 11. 000 69 r R R r F r .000 2.500 14. 000

I 10 r R R r r F .000 3. 000 14 . 000 71 r R R r F r .000 3.100 14.000 72 r R R r r r .000 4.000 14. 000

I 13 r r F r r F .000 .000 16.000 14 F R R r r r .000 .100 16.000 11 r R R F r r .000 1.000 16.000 16 F R R r r r .000 1.500 16.000

I 77 r R R r r r .000 2. 000 16.000 78 r R R r r r .000 2.100 16.000 19 r R R F F r .000 3.000 16.000

I 80 r R R r F F .000 3.100 16.000 81 F R R F r F .000 4.000 16.000

I EQUATIOW lUMBERS I 1 Y ! 11 yy 11 1 a a a a a 0

I 2 a 1 2 a 0 a 3 a 3 4 a a a 4 a I 6 a a 0

I I 0 7 8 a a a 6 a 9 10 a a a 7 a 1l 12 0 0 0 8 0 13 11 a a a

I 9 0 15 16 a 0 a 10 0 0 a 0 a a 1l a 17 18 a a a

I 12 a 19 20 0 a a Il a 21 22 a a a 14 0 23 21 0 0 0

I 11 0 25 26 a a a 16 a 27 28 a a a 17 0 29 30 a a a 18 a II 32 a a a

I 9 a 0 0 a a 0

It 20 0 33 34 0 0 0 21 0 3S 36 0 0 0

I 22 0 37 38 0 0 0 23 0 39 40 0 0 0 2t 0 H 42 0 0 0 2S 0 0 H 0 0 0

I 26 0 ., 46 0 0 0 27 0 47 48 0 0 0 28 0 0 0 0 0 0

I 29 0 49 SO 0 0 0 30 0 Sl S2 0 0 0 31 0 S3 S4 0 0 0 32 0 SS S6 0 0 0

I 33 0 S1 S8 0 0 0 31 0 S9 60 0 0 0 3S 0 61 62 0 0 0

I 36 0 63 64 0 0 0 37 0 0 0 0 0 0 38 0 6S 66 0 0 0

I 39 0 67 68 0 0 0 40 0 69 70 0 0 0 H 0 71 71 0 0 0

I 42 0 73 14 0 0 0 0 0 7S 76 0 0 0 44 0 77 78 0 0 0 4S 0 79 80 0 0 0

I 46 0 0 0 0 0 0 47 0 81 82 0 0 0 48 0 83 84 0 0 0

I 49 0 85 86 0 0 0 so 0 87 88 0 0 0 Sl 0 89 90 0 0 0 S2 0 91 92 0 0 0

I S3 0 93 94 0 0 0 S4 0 9S 96 0 0 0 SS 0 0 0 0 0 0

I 56 0 97 98 0 0 0 S1 0 99 100 0 0 0 S8 0 101 102 0 0 0

I S9 0 103 104 0 0 0 60 0 lOS 106 0 0 0 61 0 107 108 0 0 0 62 0 109 110 0 0 0

I 63 0 111 112 0 0 0 64 0 0 0 0 0 0 6S 0 113 114 0 0 0

I 66 0 l1S 116 0 0 0 67 0 117 118 0 0 0 68 0 119 120 0 0 0 69 0 121 122 0 0 0

I 70 0 123 124 0 0 0 71 0 m 126 0 0 0 72 0 127 128 0 0 0

I 73 0 0 0 0 0 0 14 0 129 130 0 0 0 7S 0 III 132 0 0 0

I 76 0 133 134 0 0 0 77 0 IlS 136 0 0 0 78 0 131 138 0 0 0 79 0 !39 110 0 0 0

I 80 0 141 142 0 0 0

I, 81 o I4l 144 0 0 0

I •• 1 PLAlE-~!X8RAJE ELEMEIT III

,.tttt','atttt.tt,t,'ttt.,tttt,.

ELENE ITS AR! PLAII STRESS

I t,ttttt,tt •••••• _.tttttt ••• tt,t.

I -ELEMEIT LOAD MOLT[PL[ERS -

LOAD !-GRAVITT %-GRAVITT 1 ,000 ,000

I -~ATER[AL PROPERT[ES -

I MAT!R[AL [,0, IOK8!R : I ![G8T (GRAV[TT LOAD) : ,000Dl100

I I (TOOIGS MOOOLOS ) : ,2960E105 o (POSS[OIS RAT[O ) : ,3000

G (S81AR MOOOLOS ) ,1138E105

I -ELIM!IT Olf[ [T[OIS -

I IL I MAt n H 13 II HI 16 n 18 M9 mCl I I I 2 3 10 11 12 19 20 21 ,38

I 2 1 3 1 I 12 13 II 21 22 23 ,38 3 I I 6 7 II 11 16 23 21 25 ,38 1 I 7 8 9 16 17 18 25 26 27 ,38 5 I 19 20 21 28 29 30 37 38 39 ,38

I 6 I 21 22 13 30 1I 32 39 10 II ,38 7 I 23 21 25 32 33 H II 12 jJ ,31 8 I 25 26 11 H 35 36 jJ II 15 .38

I 9 I 37 38 39 16 17 IS 55 56 57 ,38

10 I 39 10 II 18 19 50 \7 58 59 ,38 11 I II 11 jJ 50 51 52 59 60 61 ,38

I 12 I 13 II 15 52 53 51 61 62 63 ,38 13 I 55 56 17 61 65 66 73 74 75 ,38 II 1 57 58 59 66 67 68 75 76 77 ,38 15 1 59 60 61 68 69 70 77 78 79 ,38

I' 16 1 61 62 63 70 71 72 79 80 81 ,38

I TSE lODE IOK8!iIIG OSED PRODOCED A HALf 8AIDV[DTS or 38

I TOTAL STORAG! REQO[RED : 5859 TOTAL STORAGE AVA[LABL! : 50000

I I

.11 COICEITIATED 100AL LOADS III

lODE LOAD 1 T I 11 H II I I ,00ltOO ,00ltOO , 1lE101 ,OO EIOO ,0 01100 ,OOEIOO

I 2 I ,OO!IOO ,OO EIOO ,m102 ,001100 ,OO EIOO ,001100

I· 3 I .001100 .001+00 .10lt02 .00ltOO .001+00 .001+00 I I .001+00 .001100 .211+02 .00ltOO .001100 .001tOO I I .001100 .001tOO .lOIt02 .001tOO .001tOO .00EtOO

I 6 I .001t00 .001tOO .mt02 .001100 .001100 .001100 1 I .00£100 .001100 .101102 .001tOO .00BtOO .00BtOO 8 I .001+00 .001100 .m102 .00BtOO .001100 .001100

I 9 I .00BtOO .001100 . SUIOI .001100 .001tOO .00BtOO

FORMATIO! OF STlffllSS MATRII

I START Of SOLOTIO. Of IOOATIOIS

I III PRIIT or fIIAL DISPLACEMIITS II.

I DISPLACKMIITS fOR LOAO COIDITIOI I 10DI I Y I II n 11

I .000001100 .000001100 .000001100 .00000BtOO .000001100 .000001100

I 2 .000001100 .320111-02 .120111-02 .000001100 .000001100 .000001100 3 .000001100 .138591-02 .806851-02 .000001100 .00000BtOO .000001100 I .000001100 .514911-02 .108221-01 .000001100 .00000£100 .000001100 I .OOOOOEIOO .511811-02 .l26m-OI .000001100 .000001100 .000001100

I 6 .000001100 . 59112E-02 .114101-01 .000001100 .000001+00 .000001+00 1 .000001100 .624311-02 .151111-01 .000001100 .000001+00 .000008+00 8 .000001100 .660821-02 .110961-01 .00000£100 .000001100 .00000BtOO

I 9 .000001100 .10046H2 .182221-01 .000001100 .000001100 .00000BtOO 10 .000001t00 .00000EtOO .000001100 .000001100 .000001100 .000001100 II .000001100 -.550111-03 .162111-02 .000001100 .00000£+00 .000001100

I 12 .000001100 -.13156E-03 .40193H2 .000001100 .000001100 .000001100 Il .000001100 .352411-03 .595241-02 .00000BtOO .00000BtOO .000001100 II .000001100 .901061-03 .118481-02 .000001100 .000001100 .00000BtOO 15 .000001100 .142101-02 . 922m-02 .000001100 .00000BtOO .00000BtOO

I 16 .000001100 .188111-02 .105281-01 .000001100 .000001t00 .000001100 11 .000001100 .23IlU-02 .115461-01 .000001100 .000001100 .000001100 18 .00000BtOO .213611-02 .124911-01 .000001100 .000001100 .000001100

I 19 .000001t00 .000001100 .000001100 .OOOOOEIOO .000001100 .000001t00 20 .000001100 .645831-03 .113221-02 .000001tOO .000001100 .00000BtOO 21 .000001100 .151161-03 .232411-02 .000001100 .000001100 .000001100

I 22 .000001100 -.986211-05 .362811-02 .000001100 .00000BtOO .000001100 23 .000001100 -.122131-03 .11102!-02 .000001100 .00000BtOO .000001100 24 .000001+00 -.844081-04 .565321-02 .000001+00 .000001+00 .000001100 25 .000001100 .609831-01 .610131-02 .000001100 .000001100 .000001100

I 26 .000001100 .282641-03 .110311-02 .00000BtOO .000001100 .000001t00 21 .000001100 .5S2\8B-03 .138531-02 .000001100 .000001100 .00000BtOO 28 .00000£+00 .000001t00 .000001100 .000001+00 .000001100 .000001100

I 29 .000001100 -.341191-03 .134m-03 .000001100 .000001100 .000001+00 30 .000001100 -.222921-03 .118011-02 .000001100 .000001100 .00000ltOO 31 .000001100 -.241391-03 . 240m-02 .000001100 .000001100 .000001100 32 .000001100 -.204171-03 .309551-02 .000001100 .00000BtOO .00000BtOO

I J3 .000001100 -.144231-03 .358551-02 .000001100 .000001100 .00000BtOO 34 .000001100 -.466201-04 .403991-02 .000001100 .00000BtOO .000001100 35 .000001100 .893741-04 .428901-02 .000001100 .000001100 .00000BtOO

I 36 .000001100 .253001-03 .142191-02 .000001100 .00000ltOO .000001100 31 .000001100 .000001100 .000001100 .000001100 .00000ltOO .000001100 38 .00000BtOO .205261-03 .106m-03 .00000BtOO .000001100 .00000EtOO 39 .000001100 -.183851-03 .840231-03 .000001100 .000001100 .000001100

I 40 .000001100 -.169111-03 .152161-02 .000001100 .000001+00 .000001100 41 .000001100 -.168401-03 .183861-02 .000001100 .00000BtOO .00000ltOO 42 .000001+00 -.109961-03 .227181-02 .000001100 .000001100 .000001100

I 43 .000001100 -.303261-04 .241821-02 .OOOOOEIOO .000001100 .000001100

I 41 .000001100 .593341-04 .27 0261-02 .00000£100 .00000£+00 .000001100 45 .00000£tOO . 1427O£-Ol .2 74401-02 .000001100 .00000£tOO .00000ltOO

I 46 .00000£100 .00000£100 .000001100 .00000£tOO .00000£100 .00 000£100 47 .00000£+00 -.ll72l£-Ol .lllllE-Ol .00000£+00 .000001100 .00000£100 48 .00000rtOO -.28518£-04 . 180llE-Ol .000001100 .00000£100 .00 0001100 49 .ooooor+oo -.1 1148£-04 .91409I-Ol .000001100 .00000£100 .00000£tOO

I 50 .00 000£+00 -.69l48£-04 .12199H2 .00000£+00 .00000£+00 .000001100 51 .00000£+00 -.51129£-04 .14481£-02 .OO OOOE+OO .000001100 .00000£+00 52 .00000 £tOO -.16189£-04 . 16l1lE-02 .00000£+00 .00000£+00 .000001+00

I 5l .00000£tOO .l0489H4 . 11l89H2 .000001+00 .000001tOO .00000£+00 14 .000001100 .mllE-04 .17112H2 .000001100 .000001+00 .000001tOO 55 .000001+00 .000001100 .00000£+00 .000001100 .000001100 .0 00001+00 56 .000001100 .881591-04 .ll645Hl .000001+00 .00000£100 .000001+00

I 51 .000001+00 -.11181£-Ol .l11l61-Ol .00000£tOO .000001+00 .000001+00 58 .000001100 -.81615£-04 . 111 261-Ol .00000£+00 .000001100 .00000£+00 59 .00000£100 -.65501£-04 . 189m-Ol .00000£+00 .000001100 .000001100

I 60 .000001+00 -.280l4£-04 .10l001-O2 .OOOOOEIOO .00000£100 .000001+00 61 .00000£+00 .134101-05 .109891-02 .00000£100 .000001+00 .000001100 62 .0 00001100 . 1 14361-0 4 .12222H2 .00000£100 .000001100 .00000£+00

I 6l .00000£+00 .46080H4 .1226lH2 .00000£+00 .00000£100 .00000£100 64 .000001+00 .000001100 .000001100 .00000£100 .000001+00 .000001100 65 .00000£+00 -.62411£-04 .1lllll-0l .000001tOO .000001+00 .00000£100 66 .000001+00 .234241-04 .l9409E-Ol .00000£tOO .00 0001100 .000001100

I 61 .000001+00 -.45l22£-04 . 41l8lE-Ol .00000£+00 .00000£+00 .000001100 68 .000001+00 -.62lll£-04 . 68976£-Ol .000001+00 .000001+00 .000001+00 69 .00000£+00 -.80021E-04 . 188071-Ol .00000EtOO .O OOOOEIOO .000001100

I 70 .00000£+00 -.8l504E-04 .m8lE-Ol .00000£tOO .00000£tOO .000001+00 11 .000001+00 -.82119E-01 .10006&-02 .000001100 .000001100 .000001100 12 .00000£tOO -.1 2205£-04 .108l8H2 .00000£tOO .00000£tOO .000001+00

I 13 .00000£+00 .00000£tOO .00000£tOO .00000EtOO .00000£tOO .000001100 14 .00000£+00 -.1 2195E-04 .185m-Ol .00000£tOO .00000£tOO .00000£tOO

I 11 .000001100 -.l8101£-Ol .16819B-Ol .00000£tOO .00000£tOO .00000£tOO 16 .00000rtOO -.l4l15£-Ol .54461Hl .oooomoo .0 0000rtOO .000001100

I 11 .00000£100 -.l8028£-Ol . 514691-0l .00000£tOO .000001100 .ooooor+oo 18 .00000 £tOO -.l1511£-Ol . 186l8E-03 .00000£tOO .00000£+00 .000001100 19 .00000£+00 -.31194£-Ol .845m-03 .00000£tOO .000001100 .0 0000£tOO

I 80 .000001+00 -.l1231£-03 .91998Hl .00000£+00 .000001tOO .000001100 81 .000001+00 -.382401-03 .104411-02 .000001+00 .000001100 .000001tOO

I £LI LD' JODE Syy SII Su Sf' S(KAl) sImI AKGL£ 1------------------------------------------------------------------------

1 102.95 4.66 .00 11.7l 104. 33 3.28 6.11

I 2 10.50 -41.16 .00 8.84 11.18 -45.43 4.36 3 38.05 -94.11 .00 -.89 l8.06 -94.18 -.39

10 Il.21 2.54 .00 12.41 80.50 -64.12 42.89

I 11 15.14 -19 .5l .00 69.52 69.58 -13.11 l1.96 12 11.45 -41.60 .00 59.80 51.61 -18 .76 11.86 19 -16.49 .43 .00 -5.13 .11 -16.8l -86.20 20 -l9.82 5.10 .00 -8 .02 1.01 -41.19 -80,]0

I 21 -1.16 10 .98 .00 -11.14 21.01 -15.19 -55 .86 2 1------------------------------------------------------------------------

I IU5 -12.11 .00 8.16 11. 05 -12.88 4.18

I 4 22 .11 -80.69 .00 .8l 22 .l2 -80 .69 .46 5 8.21 -89.20 .00 -6.80 8.14 -89.67 -1.91

12 12.10 -l9.86 .00 42.51 l6.45 -6l.61 29.16

I 13 9.8l -49.58 .00 lU5 25.11 -65.51 21.69 14 6.91 -59.30 .00 21.02 16.59 -68.92 19 .60 21 -10,95 -1.54 .00 II. 10 22.50 -40.99 46.14 22 -2 .64 -18.11 .00 2l.11 14.10 -l\.61 l5 .19

I 2l 5.66 -29.40 .00 16.11 11.96 -l5.11 21.32

•• I I I I I I I I I I I I I I I I I I

1------------------------------------------------------------------------5 9.24 -85.09 .00 5.86 9.61 -85.45 3.11 6 U4 -86.11 .00 -.35 U4 -86.11 -.22 7 - .56 -88.33 .00 -5.66 -.20 -88.69 -3.61

14 6.64 -58.11 .00 20.7S 12.70 -64.17 16.27 15 UO -63.67 .00 14.14 7.09 -66,65 11.61 16 LS6 -68.92 .00 9.23 2.75 -70.11 7. 31 2J U4 -31.74 .00 26.20 17.88 -45.51 21.8( 24 3.86 -40.63 .00 19.98 11.52 -48.28 20.97 21 3.68 -(9.51 .00 11.68 7.46 -SJ.JO IUS

4 1------------------------------------------------------------------------7 .51 -81.11 .00 3.9l .69 -81.28 2.51 8 .02 -89.29 .00 -.31 .02 -89.29 -.22 9 -.17 -91.18 .00 -3.70 -.32 -91.63 -2.32

16 1.70 -68.15 .00 1.13 1.41 -68.81 5.77 11 .60 -11.01 .00 1.85 .71 -74.12 1.18 18 -.50 -19.81 .00 -.51 -.50 -19.87 -.37 15 1.89 -49.19 .00 12.76 5.85 -51.15 13.05 26 1.18 -58.73 .00 8.48 1.36 -59.901.90 11 -.53 -68.26 .00 5.11 -.15 -68,65 U9

1------------------------------------------------------------------------19 11.90 -8.41 .00 .49 11.91 -8.43 1.38 10 -4.27 -16.59 .00 -1.16 -4.16 -16.10 -5.32 21 -20.44 -24.16 .00 -3.32 -18,6( -26.56 -28.45 28 -7.53 -2.86 .00 31.97 16.86 -31.25 47.09 29 -1.10 -8.98 .00 30.32 22.30 -38.31 41.11 30 -6.61 -15 .10 .00 28.16 17.59 -39,36 40.74 37 -26.96 1.11 .00 -2.91 3.00 -11.26 -8U5 38 -9.93 -1.36 .00 -1.61 .65 -11.94 -66.13 39 1.11 -5.43 .00 -6.11 10.01 -8.39 -23.61

6 1------------------------------------------------------------------------21 -11.08 -13.55 .00 22.91 9.10 -36.12 41.31 22 -11.99 -22.09 .00 22.29 5.82 -39.90 38.61 23 -9.89 -30.64 .00 20.60 2.80 -43.33 31.63 30 -7.62 -13.25 .00 16.00 5.81 -26.68 (0.02 31 -6.26 -17.41 .00 15.39 4.11 -28.24 31.99 32 -1.91 -21.10 .00 13.69 2.16 -29.31 29.24 39 -1.16 -IU( .00 12.06 6.31 -20.17 31.98 40 -.54 -11.85 .00 11.14 UO -19.69 30.86 41 .01 -12.76 .00 9.15 5.33 -18.02 2S.32

1 1------------------------------------------------------------------------23 -S.S2 -28.66 .00 22.20 5.19 -42.91 32.S0 24 -5.58 -36.52 .00 20.01 4.24 -4U4 26.14 25 -2.64 -44.38 .00 16.S3 J.JO -50.32 lU( 32 -4.19 -21.83 .00 13.21 2.56 -28 .98 2S.44 33 -3.0( -25.17 .00 11.01 l.42 -30.23 22.04 31 -l.4S -29.11 .00 1.83 .55 -31.7( lUI 11 -.66 -11.99 .00 9.15 4.21 -19.92 26.84 42 -.49 -15.01 .00 7.55 2.12 -18.23 23.05 43 -.32 -15.03 .00 Ul .88 -16.23 11.35

8 1------------------------------------------------------------------------21 -2.11 -44 .08 .00 12.73 1.11 -41.66 15.12 26 -1.00 -(9 .11 .00 8.80 .11 -11.31 9.92 21 .42 -15.41 .00 UI .11 -55.16 4.13 34 -1.30 -30.00 .00 8.33 .94 -32.21 11.06 3S -.51 -32.11 .00 4.10 .08 -33.01 1.11 36 .21 -34.82 .00 -.35 .28 -34.83 -.51 43 -.19 -15.93 .00 6.44 2.11 -18.23 19.65 44 - .03 -15.05 .00 2.51 .38 -15.46 9.21 45 .13 -IUl .00 -2.24 .41 -14.12 -S.69

9 1------------------------------------------------------------------------

I 37 2.20 -5.43 .00 .51 2.24 -5. 47 4.02 38 -4.59 -6 .81 .00 -.38 -4.53 -6.88 -9.42 39 -11.39 -8 .19 .00 -I. 01 -7. 87 -11.11 -13.14

I 46 -3.71 -1.31 .00 3.69 11.23 -16.25 41.51 47 -3 .49 -3.60 .00 12.77 9.22 -16 .31 44.87 48 -3.27 -1.90 .00 12.08 1.57 -16. H 41.89

I 55 -9.62 2.82 .00 -1.22 2.94 -9.73 -84.44 56 -2.38 -.39 .00 -2 .14 .97 -3.75 -57.46 51 4.85 -3 .61 .00 -2.83 5.71 -4.41 -16.87

I 10 1------------------------------------------------------------------------

39 -5 .90 -4.12 .00 11.92 6.94 -16.97 41.14 40 -1.20 -9 .12 .00 11.70 5.29 -18.61 39.06

I 41 -2.50 -14.12 .00 1D.65 3.83 -20.44 30.69 48 -3.03 -4.87 .00 6.68 2.79 -10.70 41.09 49 -2.12 -6.18 .00 6.46 2.49 -11.18 35.48 \0 -1.20 -8.28 .00 1.41 1.12 -11.21 28.39

I \7 -.16 '\.61 .00 1.19 2.4\ -8.23 29.6\ 58 -.03 -4.03 .00 4.36 2.17 -6.83 32.70 \9 .10 -2.15 .00 3.32 2.38 -4.73 31.11

I II 1------------------------------------------------------------------------

41 -2.08 -11.76 .00 8.48 2.84 -16.69 3U5 42 -1.18 -14.15 .00 1.11 2.13 -17.77 24.08 43 -.28 -J 1.15 .00 5.94 1.60 -19.03 11.57

I 50 -1.24 -8 .29 .00 5.63 1.87 -11.11 28.98 \1 -.72 -9 .36 .00 4.56 1.24 -11.32 23.27 52 -.20 -10.43 .00 3.08 .66 -11.29 15. \3

I 59 -.40 -4.82 .00 4.30 2.22 -7.44 31.39 60 -.26 -1.21 .00 l.2l 1.Il -6.06 29.01 61 - .12 -l. 72 .00 1.75 .\9 -Ul 22.10

I 12 1------------------------------------------------------------------------

43 -.36 -16.18 .00 1.00 .60 -11.11 13. 41 14 -.17 -17.19 .00 2.16 .11 -17 .83 7.93 15 .02 -18.79 .00 .71 .01 -18.82 2.16

I \2 -.26 -10.12 .00 3.30 .12 -11.10 lUI 53 -.10 -10.90 .00 1.76 .18 -11.18 9.02 51 .06 -11.38 .00 .01 .06 -11.38 .05

I 6! -.1 7 -1 .67 .00 2.69 1.09 -5.93 25.07 62 -.03 -1 .32 .00 1.15 .26 -1.60 14.10 63 .11 -3.96 .00 -.60 .20 -1.05 -8 .21

Il 1------------------------------------------------------------------------

I 55 2.66 -3.08 .00 .72 2.75 -3.17 7.09 56 -.01 -2.39 .00 .37 .02 -2.15 8.86 57 -2 .7\ -1.10 .00 .38 -1.58 -2.87 72.03

I 61 -3.13 -.97 .00 5.79 3.84 -7.93 50 .28 6\ -2.95 -1.10 .00 5.41 3.1l -7.80 18.30 66 -2.78 -2 .12 .00 5.44 2.84 -8.05 lUI

I 13 -8.91 1.11 .00 -.6\ 1.18 -8.96 -86.29 H -5.87 -1.01 .00 -1.00 -.81 -6.06 -78 .78 75 -2 .82 -3.1\ .00 -1.00 -1.97 -1.00 -40.27

14 1--------_·_------------------------------------------------.------------

I \7 -.19 -1.10 .00 5.07 1.28 -5 .87 13.27 \8 -.\8 -3.63 .00 1.89 3.02 -7.23 3U4 \9 -.67 -6.16 .00 1.12 1.51 -8.37 28.18

I 66 -2.23 -1.60 .00 1.00 2.09 -5.92 47.27 67 -1.60 -1.15 .00 3.82 2.15 -5. \0 11.17 68 -.98 -1.90 .00 3.05 1.6\ -1.12 10.72

I 7\ -3.98 -2 .09 .00 .05 -2 .09 -3.98 88.50 16 -2.63 .14 .00 . . 12 .1\ -2.63 -81.13 17 -1.28 2.31 .00 -.89 2.58 -1.19 -16 .96

1\ 1------------------------------------------------------------------------

I \9 -.\6 -3 .\6 .00 3.19 2.02 -6.13 31.21

I ~. 60 -.40 -4.42 .00 3.28 1.44 -6.26 29.26 61 -.25 -5 .29 .00 2.56 .83 -6.36 22.76

I 68 -1.04 -1.94 .00 2. 67 1.21 -4.19 40.25 69 -.63 -1.91 .00 2. 16 .96 -3.56 36.11 10 -.22 -2.00 .00 1.44 .58 -2.80 29.17 77 -1.53 -.32 .00 .52 - .13 -1.72 69 .19

I 78 - .86 . 48 .00 .01 .48 -.86 89 .69 79 -. 20 1.29 .00 -.71 1.57 -.48 -68 .13

16 1------------------------------------------------------------------------

I 61 -.22 -4.35 .00 1.82 .47 -5 .03 20 .69 62 - .10 -4.21 .00 1.22 .24 -4.15 15.40 63 .02 -4.07 .00 .59 .10 -4.15 8.08

I 70 -.26 -2.05 .00 1.26 .39 -2.70 27.27 71 - .10 -1.76 .00 .61 . 13 -1.99 19.42 12 .06 -1.16 .00 .04 .06 -1.16 1.32 79 - .30 . 24 .00 .55 .58 -.64 58.05

I 80 - . 10 .69 .00 -.05 .69 -.10 -86.63 81 .10 US .00 - .68 l.48 -.24 -63 .83

I I I I I I I I I I I I I

I ~


ppendi B

Part One Reaction v Displacement Grapb '

Only SpecImens three, four, and six used the aforementtoned thIrd LVDT in

contact with the column flange. For these specImens- ali of whIch are denoted by

BS#-the corrected values refer to the actual values read from L VDT' one and two WIth

the value read from L VDT three subtracted from them. These three specImen , and thus,

theIr respective graphs give the "be t" load/displacement data of all tests run dunng pan

one

Neganve displacements mean that the L VDT pin was movmg out from Its neutral

position. Positive displacements mean the pin was being pushed inward. In other words,

negative displacements correspond to the web moving away from the L VDT and posItive

displacements correspond to the web moving toward the L VDT.

The graphs of BS4-L VDT I and BS6-L VDT I are shown rescaled on longer a;<es

for the purpose of companng these graphs to their counterpans from Pan Two

40

I I I I I SEAT REACTION v DISPLACEMENT

I 8S1 ; LVDT1

160

I 140

I 120 \ \

I ~

li 100

i 80 t I (11

I ~ 60 '"

40 I I 20

I 0

I -0.2 -0.15 -0.1 -0.05 0 Displacement (in.)

I I I I 41

I


160

140

120

~

li 100 ~ ........ c: 80 0 .. u ('0 Q) 60 r ex:

+

40 -

20 -

0 0

SEAT REACTION v DISPLACEMENT 8S1 ; LVDT2

0.05

, I

t'

,/

,

0.1 0.15 0.2 0.25 Displacement (in.)

42

0.3 0.35

., I I I I I I I I I I I I I I I I I I

160 ,

140 ~

120

...... ~ 100

~ 80 1 'fi J !II (I) 60 a:::

40

20

0 -0.25

SEAT REACTION v DISPLACEMENT 882; LVDT1

I

\

-0.2 -0.15 -0.1 -0.05 Displacement (in.)

43

o

I. I I I I I I I I I I I I I I I I I I

SEAT REACTION v DISPLACEMENT 8S2; LVDT2

160 ----~--------------------------~

140

120

........ ~ 100 ~ t ....... § 80 -'U C\l

~ 60

40 .,.

20 1 1/

,

/'

/

I

I

I

O --~~~+_~+-~+-~~~~~~~~

-0.02 0 0.02 0.04 0.06 0.08 0.1 0.12 0.14 Displacement (in.)

44

•••


SEAT REACTION v DISPLACEMENT 8S3; L VDT1 corrected

160 ---------------_

140 -

120

~

~ 100

~ 80 1 u t (II

(I) 60 -0::

40

20

0 ~~-+-~~~-~~_+-~~--_4

-0.12 -0.1 -0.08 -0.06 -0.04 -0.02 o Displacement (in.)

45

I · , I

I I I I I 160

I 140

I 120 -

~

I ~ 100 ~ -

I c 80 -0 n + ro Q) 60 -

I a::

40 t I

20 T

I 1 0

I 0

I I I I I


,

/ (

0.1 0.2 0.3 Displacement (in .)

46

0.4


160

140

120

---(/J 100 0-~ -c 80 ..-0 :g <tI Q) 60 + a::

40 +

20 I

0

-0.05

SEAT REACTION v DISPLACEMENT 8S4; LVDT1 corrected

-0.04 -0.03 -0.02 -0.01 Displacement (in.)

47

o


SEAT REACTION v DISPLACEMENT 8S4; LVDT1 corrected/rescaled

160 ------------------------

140

120

~

~ 100 }

§ 80 ~ C1I Q) 60 + a:

40 +

I 20

0 L---~--+---~--4---~--~---r--~--~

-0.45 -0.4 -0.35 -0.3 -0.25 -0.2 -0.15 -0.1 -0.05 0 Displacement (in.)

48


160

140

120

~

~ 100 :i: ~ t

c 80 • 0 :p u co Q) 60 ~ 0:

40

20

0

0


I

0.1 0.2 0.3 0.4 Displacement (in .)

49

0.5

I I I I I SEAT REACTION v DISPLACEMENT

I 8S5; LVDT1

160

I 140

I 120

-I ~ 100 ~ -

I c: 80 -0 ~ U 10 Q) 60 -

I a::: t

I 40 T

20

I 0

I -0.2 -0.15 -0.1 -0.05 0 Displacement (in.)

I I I I 50

I

I ~


160

140

120

.-. (/j 100 a. ~ ......, c 80 0

n III Q) 60 -a:::

+

40 -

20

0 -0.05


,/

/ I

0 0.05 0.1 0.15 Displacement (in.)

51

0.2 0.25


160

140

120

---. .~ 100 ~ -c 80 -0 :;:; u (1l Q) 60 -0:::

40 -

20 ~ o I -0.1


-0.08 -0.06 -0.04 Displacement (in.)

52

-0.02 o


SEAT REACTION v DISPLACEMENT 8S6; LVDT1 corrected/rescaled

160 ---------- ------~

140

\ 120

t

40 -

20 -

\ \

\ \ \

O +---+--~-~--r--~--~r---~

-0.35 -0.3 -0.25 -0.2 -0.15 -0.1 -0.05 o Displacement (in.)

53


160

140

120

~

<I) 100 .9-~ -c: 80 0 n co Q) 60 -0::

40

20

0

0

I

SEAT REACTION v DISPLACEMENT 8S6; L VDT2 corrected

/

< r

I'

0.05 0.1 0.15 0.2 0.25 0.3 0.35 Displacement (in.)

54

It I I I I I I I I I I I I I I I I I I

Appendix C

Pan Two Reaction v Displacement Grapbs

Graphs for all tests except Test Three are included here. The displacement data

for Test Three was lost when the computer reading the L VDT's crashed. All tests

tncluded L VDT 3. which was placed on the left nange to measure ngld body rotal1on of

the column. The graphs. therefore, depict only displacement of the column web and not

any of the rigid body movement of the column which ma have 0 curred, which ome

graphs tn Part One included.

In the cases where ngid body motion was accounted for (subtracted from the total

displacements in the web), the graphs of Parts One and Two match up quite well. In fact,

the graphs from Pan Two are a continuation of the same curve from Part One after

unloading occurred.

As mentioned previously. positive displacements correspond to the portion of the

web being monitored moving toward the L VDT and negative displacements correspond

to the ponion of the web being monitored movtng away from the L VDT.

55

I ~


140

120

100 -In a. 6 80 c o U 60 C1l Q)

a::: 40 -

20


o --"---- ~S--_ +--------'1--- _

-0.4 -0.3 -0.2 -0.1 Displacement (in.)

56

o

I ~


....... III a. ~ -c 0 ~ u ro Q)

a:::

140

120

100

80 -

60 I

40 -

20 -


:it

/ 7"

I ;r;

--- ~ ... z

l o -0 0.05 0.1 0.15 0.2

Displacement (in.)

57

0.25

.' • I I

• • I

• I I

• I I I I

• I I I


200 ------------------------------~

150

-III .~ .':iI:. -§ 100 U co Q)

c::

50

+

O ~i------~--~--~~--~--~--~~

-0.2 -0.15 -0.1 -0.05 o Displacement (in.)

58

I ~


200

150

-III a. :i: ~

§ 100 U co Q)

0::

50

t


Approx. Buckling Load

I 1301< 1/

/ o ~-+-- ---t--+--l----+---L--<I---*'-----+-- _----+---1

-0.04 -0.03 -0.02 -0.01 0 0.01 0.02 Displacement (in.)

59

•• • • • • • • • • I

• I

• • • • I

• •

160

140

120

-.9. 100 ..:.:: -c 80 0 .. U III

60 ..,. Q)

cr::

40 -

20 -

0

-0.5


:f- --.o.--E '"

~

~

-0.4 -0.3 -0.2 -0.1 0 Displacement (in.)

60

I' 1 I I I I I 160

I 140

120

I - ,

2. 100 -

I ~ ....-c 80 0

I n t (0

60 .,.-Q)

a::

I 40 ... t

I 20 ~

I 0

0

I I I I I


z~ -z

x

x

/ 0.05 0.1 0.15 0.2 0.25

Displacement (in .)

61

0.3

I· I I I I I SEAT REACTION v DISPLACEMENT

I 200 8S5; LVDT1

180 ~

I 160

I 140 -(/) ·9-120

I ~ - , ~ 100 ~

:;:; <J

I III 80 -Q)

c::: 60 T

I 40 ...

I 20

0

I -0.25 -0.2 -0.15 -0.1 -0.05 0 Displacement (in.)

I I I I 62

I

I ~

I I I I I I 200

180

I 160

I 140 -(f) ·9-120

I .Yo ........ + § 100 ..

I u m 80 -Q)

0:::

I 60 T 40 -

I 20

0

I 0

I I I I I


7.

0.05 0.1 0.15 0.2 Displacement (in .)

63

0.25 0.3

I ,· e ~.


SEAT REACTION V DISPLACEMENT BS6; LVDT1

180 -----------------,

160

140

(j)120 -a. ~100 .J..

§ j

'13 80 -

~ 60 1 40 1 20

~ __ -'K

-------- ~ po-:~ _

\

O ~~~~~~~-~+_--~~-+ __ ~ -0.35 -0.3 -0.25 -0.2 -0.15 -0.1 -0.05 o

Displacement (in.)

64

I , .


180

160

140

SEAT REACTION V DISPLACEMENT 8S6; LVDT2

".Ii. -I /..

-120 Ul ! c. 6100 / c 0

n ro Q)

a:::

'F-80 t x

60 I

40

20

o L-3~~-+~4-~~-+~~~~~ -0.05 0 0.05 0.1 0.15 0.2 0.25 0.3 0.35

Displacement (in.)

65

I ~


ppendix 0

Beam Web tress and train Grapb

The followmg graphs depIct stress and stram data gathered from the stram gage

rosenes mounted on the reaCllon beam web dunng Part One of this phase of teSllng. The

data used are from Tests Four and FIve. These tests gave the best stram data smce m

both cases the strain gages attached to the beam web were new and unstrained.

The first graph shows the compressIve stress distnbullon m the beam web WIth

respect to the poSitIOn of the rosette on the beam. The next graph ho\ the stress at

each rosette position as a function of the reaction at the seated conneCllon. The stresses

where computed usmg equations which assume linear elastic behavior from

Expertmenral Stress AnalysIs by Dally and Riley. This is why only the pOints \~here the

matenal is assumed to be In the linear elastic range, or very near It, where plotted for

stress data.

The later graphs sImply show how the beam web deformed at each ro ette

posItIon as the load on the connection Increased. One can relate thIS deformation to

stress if the proper equations relating stress and strain are used.

As can be seen by observing the graphs, Beam web yielding IS not a problem

under servIce conditions.

66

I· .

I I I I 1 I 1 I I I I I I I 1 I 1 1

50 ---I/)

~40 I/) I/)

~ 30 en

220 co :::J

~ 10

STRESS IN BEAM WEB v REACTION BS4

Service Load

.-- / -

---

()

o -~;-;;;:! ~==::;:::=\:::=:;:::====:=-o 10 20 30 40 50

Reaction (kips)

rosette 1 rosette2 rosette3 J

67

60

I· . I I I I 1 I 1 I I I I 1 I I I I I I

PRINCIPAL COMPo STRESS v BEAM POS.

40

~30 C/) C/)

a.>

t5 20 ro c. u .S 10 .... c.

in the linear range for BS4

-

•

~-=:.....---=::;;- - ---=-----...: -0 --

o 1 2 3 4 position on beam (in .) 0 = end

~ 8.45 kips ...0... 14.44 kips • 22.03 kips ~ 30.66 kips - 37.78 kips - 45.37 kips

68

5


SEAT REACTION v PRINCIPAL COMPo STRAIN

160 8S4; ROSETTE 1 ,:

140 :J ;:

):

120 6 ......... 7-en

:.d: ,0.100 .r ~ "-' ~

c 80 ~ 0

~ -u co 60 Q)

a:: :z.

40 -'J!

:;(

z

20 z z

z

o '" ---<

0 1000 2000 3000 4000 5000 6000 7000 Microstrain

I

69

I' 1 I I I I I I I I I I I 1 I I I I 1

•


......... en

160

140

120

,0.100 ~ -,5 80 -() 13 60 cr:

40

20 z z ~

z z

Z

/.

z

BS4; ROSEnE 2

z

o ~;---o 1000 2000 3000 4000 5000

Microstrain

70

6000 I

I ~



......... (/)

160 -

140

120

,0.100 ~ '-"

§ 80 :.;:; u m 60

0::: z 40 - :t

- z 20 :;:

z '""' o ~-

8S4' ROSEnE 3

o 500 1000 1500 2000 2500 3000 Microstrain

71

.' I I I I

• I I I I I I I I I I I I I


..-.. en

160

140

120

,0.100 .:.:: --§ 80

'~

u m 60 ~

40 - J! Z

• ;i!

20 ;z .z.

8S5; ROSETT=--..:-E1 __

, t

,r'

z ;it

O ~~-------------------~

o 1000 2000 3000 4000 5000 Microstrain

72

I· •

I ~



160 BS5; ROSEnE 2

140 ,.

z-120 ;;:-

-If) ,0.100 ~ z '-" 'Z C 80 7-0

:;:; u z co 60 7-Q)

0:: '$.

40 z

z 20 '

.%

o '!: ....

0 2000 4000 6000 8000 Microstrain

73

I 1 V1



..-.. en

160

140

120

,0.100 ~ ---§ 80 :z ()

m 60 c::

40 ! • f

20 r :t

o t~o

8S5; ROSETTE 3

-, -.

500 1 000 1500 2000 2500 Microstrain

74


REFEREN E

I. Ellifrm, D., and T. Sputo, "Stiffened Seated Connections to Column Webs: Phase One", University of Florida Research Repon, December 1989.

_ Ellifrin, D., and T Sputo, "SlIffened Seated Connecllons to Column Webs: Phase Two", University of Florida Research Repon, December 1990.

3. Dally,l. and Wilham F RJiey, Experimental Stress AnalySIS, McGraw-Hill , Inc , 1965

4 Blodgett, O., Design of Welded Structures, James F. Lincoln Arc Welding Foundallon. Cle~eland, OH. 1966

5 merlcan Institute of teel Construction, Inc., Manual of Steel Con tructlon. Allowable Stress Design, Ninth Edition, Al C, Chicago, 11, 1989

75

I , : .. I l

I 1 I 1 I 1 1 I I 1 1 I I I I I I

.Ii i-~ w= ' STIFFENED EA TED CONNECTION ~= TO COLUMN …...stiffened ea ted connection to column...

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Transcript of .Ii i-~ w= ' STIFFENED EA TED CONNECTION ~= TO COLUMN …...stiffened ea ted connection to column...